A calculation method and system for fuel consumption of a relative motion configuration of a water droplet configuration

Abstract

The present invention provides a method and system for calculating fuel consumption of a relative motion configuration of a water droplet configuration, which relates to the technical field of design method research. The method includes obtaining the operation data of a target aircraft and the operation data of a tracking aircraft; determining the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft; judging whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state; if they can form a water droplet configuration, determining the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft. This method can not only obtain more accurate calculation results, but also directly obtain the fuel consumption for maintaining the relative motion configuration according to the orbital elements of the spacecraft. The calculation is stable, convenient, accurate, and has a clear physical meaning and is easy to understand, and is applicable to practical engineering applications.

Description

Technical Field

[0001] The present invention relates to the technical field of design method research, and more particularly, to a method and system for calculating fuel consumption of a relative motion configuration of a water droplet configuration. Background Art

[0002] The water droplet configuration refers to the relative motion trajectory of a spacecraft to achieve a water droplet configuration relative to another spacecraft by applying control at specific position points. The relative motion configuration of the water droplet configuration can not only keep two spacecraft in a long-term relative position in the radial direction with each other by consuming less energy, but also has a fly-around period less than the natural period of the orbit if a fly-around of the water droplet configuration is formed. Therefore, it has important practical value for space applications and the targeted research is relatively in-depth.

[0003] Traditional research methods are based on the Hill equation to carry out analysis and research under various application conditions, that is, research is carried out according to the motion equation obtained by linearizing and simplifying the relative motion equation of two spacecraft. This research and calculation method not only brings loss of calculation accuracy, resulting in the difficulty of directly applying the analysis and calculation results in engineering practice, but also because of this technical route based on the relative motion equation of two spacecraft, the orbital characteristics of the spacecraft itself are discarded, and the intuitive physical characteristic spacecraft orbit problem is transformed into an unintuitive mathematical problem, which affects the understanding of the mechanism to a certain extent. At the same time, because the analysis basis is not the orbital elements of the aircraft, it causes certain inconvenience in practical applications based on orbital elements. For the water droplet configuration, there is a clear corresponding relationship between the fuel consumption for configuration maintenance and the orbital elements of the two spacecraft. The research based on the linearization of the relative motion equation cannot give the relationship between the orbital elements and the fuel consumption for configuration maintenance. Summary of the Invention

[0004] The purpose of the present invention is to provide a method for calculating fuel consumption of a relative motion configuration of a water droplet configuration, which calculates the fuel consumption for maintaining the relative motion configuration of the water droplet configuration according to the orbital elements of the spacecraft. Compared with the traditional linearization method of the relative motion equation, it has the advantages of clear physical meaning, high calculation accuracy, direct and convenient application.

[0005] Another purpose of the present invention is to provide a system for calculating fuel consumption of a relative motion configuration of a water droplet configuration, which has all the beneficial effects of the above-mentioned method for calculating fuel consumption of a relative motion configuration of a water droplet configuration.

[0006] The embodiments of the present invention are implemented as follows:

[0007] In a first aspect, an embodiment of the present application provides a method for calculating fuel consumption of a relative motion configuration of a water droplet configuration, which includes the following steps: obtaining the operation data of a target aircraft and the operation data of a tracking aircraft, wherein the operation data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft orbit and the geocentric distance at the apogee of the tracking aircraft orbit; determining the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft; judging whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state; if a water droplet configuration can be formed, determining the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft.

[0008] This method for calculating fuel consumption of the relative motion configuration of the water droplet configuration can not only obtain more accurate calculation results than traditional methods, but also directly obtain the fuel consumption for maintaining the relative motion configuration according to the orbital elements of the spacecraft. The calculation is stable, convenient, accurate, and has clear physical meaning and is easy to understand, which is applicable to practical engineering applications.

[0009] In some embodiments of the present invention, in the step of determining the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft, it includes: when the motion configuration of the target aircraft and the tracking aircraft specializes into an elliptical configuration, and at this time, the fuel consumption for maintaining the configuration is zero; when judging whether the target aircraft and the tracking aircraft can form a water droplet configuration; wherein, is the geocentric distance at the perigee of the tracking aircraft orbit, is the geocentric distance at the apogee of the tracking aircraft orbit, r T is the geocentric distance of the operation orbit of the target aircraft.

[0010] In some embodiments of the present invention, in the step of judging whether the target aircraft and the tracking aircraft can form a water droplet configuration, it further includes: determining the semi-major axis, eccentricity, semi-latus rectum, perigee angular velocity, and apogee angular velocity of the tracking aircraft based on the operation data of the tracking aircraft and the gravitational constant of the celestial body; determining the angular velocity of the target aircraft based on the operation data of the target aircraft and the gravitational constant of the celestial body; if the apogee angular velocity of the tracking aircraft is greater than the angular velocity of the target aircraft or the perigee angular velocity of the tracking aircraft is greater than the angular velocity of the target aircraft, it is judged that the target aircraft and the tracking aircraft cannot form a water droplet configuration.

[0011] In some embodiments of the present invention, in the steps of determining the semi-major axis of the tracking vehicle, the eccentricity of the tracking vehicle, the semi-latus rectum of the tracking vehicle, the angular velocity at the perigee of the tracking vehicle, and the angular velocity at the apogee of the tracking vehicle based on the operation data of the tracking vehicle and the gravitational constant of the celestial body, and determining the angular velocity of the target vehicle based on the operation data of the target vehicle and the gravitational constant of the celestial body, it includes: The semi-major axis of the tracking vehicle is: The eccentricity of the tracking vehicle is: The semi-latus rectum of the tracking vehicle is: The angular velocity at the perigee of the tracking vehicle is: The angular velocity at the apogee of the tracking vehicle is: The angular velocity of the target vehicle is: Wherein, a C is the semi-major axis of the tracking vehicle, e C is the eccentricity of the tracking vehicle, P C is the semi-latus rectum of the tracking vehicle, ω max is the angular velocity at the perigee of the tracking vehicle, ω min is the angular velocity at the apogee of the tracking vehicle, ω T is the angular velocity of the target vehicle, μ e is the gravitational constant of the celestial body.

[0012] In some embodiments of the present invention, in the step of determining the fuel consumption for configuration maintenance based on the operation data of the target vehicle and the operation data of the tracking vehicle if a water droplet configuration can be formed, it includes: determining the smooth point and the direction switching point of the water droplet configuration based on the operation data of the target vehicle and the operation data of the tracking vehicle; determining the radial velocity component of the tracking vehicle based on the smooth point and the direction switching point of the water droplet configuration.

[0013] In some embodiments of the present invention, in the step of determining the smooth point and the direction switching point of the water droplet configuration based on the operation data of the target vehicle and the operation data of the tracking vehicle, it includes: when the smooth vertex of the water droplet configuration is at the bottom and the direction switching point is at the top, and at this time the radial velocity component v r of the tracking vehicle is Wherein, When the smooth vertex of the water droplet configuration is at the top and the direction switching point is at the bottom, and at this time the radial velocity component v r of the tracking vehicle is Wherein,

[0014] In some embodiments of the present invention, in the step of determining the fuel consumption for configuration maintenance based on the operation data of the target vehicle and the operation data of the tracking vehicle, it further includes:

[0015] Determining the required velocity increment and the fuel quantity required for a single-stage rocket based on the radial velocity component of a tracking vehicle, wherein the radial velocity component Δv of the tracking vehicle is Δv = 2|v r The fuel quantity m required for a single-stage rocket fuel is wherein, m structure is the vehicle weight, P sp is the specific impulse of the engine (in seconds), and g is the acceleration due to gravity.

[0016] In some embodiments of the present invention, in the step of determining the fuel consumption for configuration maintenance based on the operation data of the target vehicle and the operation data of the tracking vehicle, it further includes: determining the fuel consumption for the configuration maintenance according to the fuel quantity required for the single-stage rocket, the relative motion period of the water droplet configuration, and the configuration maintenance time.

[0017] In some embodiments of the present invention, when the true anomaly difference Δf of the tracking vehicle flying from the smooth vertex of the water droplet configuration to the switching point of the relative motion trajectory direction down satisfies the following equation

[0018]

[0019] wherein,

[0020]

[0021]

[0022]

[0023]

[0024]

[0025] wherein, Δf down can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf down = 90°, and after Δf down is solved, there is

[0026]

[0027] When the true anomaly difference Δf of the tracking vehicle flying from the switching point of the relative motion trajectory direction to the smooth vertex of the water droplet configuration up satisfies the following equation

[0028]

[0029] wherein,

[0030]

[0031]

[0032]

[0033]

[0034]

[0035] where Δf up can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf up = 90°, Δf up After being solved, there is

[0036]

[0037] Then, during the configuration holding time, the number N of times of configuration holding control is

[0038]

[0039] Then, the fuel consumption for configuration holding is

[0040]

[0041] where, T keep is the configuration holding time.

[0042] In a second aspect, an embodiment of the present application provides a system for calculating the fuel consumption of a relative motion configuration of a water droplet configuration, including: a data acquisition module, configured to acquire the operation data of a target aircraft and the operation data of a tracking aircraft, where the operation data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft orbit and the geocentric distance at the apogee of the tracking aircraft orbit; a configuration state determination module, configured to determine the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft; a judgment module, configured to judge whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state; a calculation module, configured to determine the fuel consumption for configuration holding based on the operation data of the target aircraft and the operation data of the tracking aircraft.

[0043] Compared with the prior art, the embodiments of the present invention at least have the following advantages or beneficial effects:

[0044] The traditional method for calculating the fuel consumption of the relative motion configuration of the water droplet configuration can not only obtain more accurate calculation results, but also directly obtain the fuel consumption for maintaining the relative motion configuration based on the orbital elements of the spacecraft. The calculation is stable, convenient, accurate, and has a clear physical meaning for easy understanding, making it suitable for practical engineering applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0046] Figure 1 Schematic diagram of the application scenario of a system for calculating the fuel consumption of the relative motion configuration of the water droplet configuration provided by an embodiment of the present invention;

[0047] Figure 2 Flowchart of a method for calculating the fuel consumption of the relative motion configuration of the water droplet configuration provided by an embodiment of the present invention;

[0048] Figure 3 Block diagram of the structure of a system for calculating the fuel consumption of the relative motion configuration of the water droplet configuration provided by an embodiment of the present invention;

[0049] Figure 4 Schematic diagram of the relative motion trajectory of the tracking vehicle in the water droplet configuration provided by an embodiment of the present invention;

[0050] Figure 5 Schematic diagram of the definition of the radial and along-track directions of the vehicle orbit provided by an embodiment of the present invention.

[0051] Reference numerals: 100 - System for calculating the fuel consumption of the relative motion configuration of the water droplet configuration; 110 - Processing device; 120 - Network; 140 - Storage device; 150 - Terminal device; 111 - Data acquisition module; 112 - Configuration state determination module; 113 - Judgment module; 114 - Calculation module. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0052] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. Usually, the components of the embodiments of the present application described and illustrated in the drawings here can be arranged and designed in various different configurations.

[0053] Accordingly, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but merely represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts fall within the scope of protection of the present application.

[0054] It should be noted that like reference numerals and letters denote like items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. At the same time, in the description of the present application, if terms such as "first", "second", etc. appear, they are only used for distinguishing descriptions and cannot be construed as indicating or implying relative importance.

[0055] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, if terms such as "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, a process, method, article or device including a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including one..." does not exclude the presence of another identical element in the process, method, article or device including the said element.

[0056] In the description of the present application, it should be noted that if terms such as "upper", "lower", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of this application is usually placed during use, it is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation to the present application.

[0057] In the description of the present application, it should also be noted that unless otherwise clearly specified and limited, if terms such as "set", "connect" are understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0058] The following will describe in detail some embodiments of the present application with reference to the accompanying drawings. Without conflict, the various embodiments and the various features in the embodiments described below can be combined with each other.

[0059] Embodiment

[0060] Figure 1 FIG. 1 is a schematic diagram of an application scenario of a fuel consumption calculation system 100 for a relative motion configuration of a water droplet configuration according to some embodiments of the present application.

[0061] As Figure 1 shown, the fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration may include a processing device 110, a network 120, a memory, and a terminal device 150.

[0062] The fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration can assist in the calculation of the fuel consumption of the relative motion configuration of the water droplet configuration. For example, it can be used to directly obtain the fuel consumption for maintaining the relative motion configuration of the water droplet configuration based on the main characteristic parameters of the orbit, improving the calculation accuracy, and the calculation is stable, convenient, accurate, and has a clear physical meaning and is easy to understand, and is applicable to actual engineering applications. It should be noted that the fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration can also be applied to other devices, scenarios, and application programs that require aircraft fuel consumption calculation, which is not limited herein. Any device, scenario, and / or application program that can use a fuel consumption calculation method for the relative motion configuration of a water droplet configuration included in the present application is within the protection scope of the present application.

[0063] The processing device 110 can be used to process information and / or data related to the fuel consumption calculation of the relative motion configuration of the water droplet configuration. For example, the processing device 110 can obtain the operation data of the target aircraft and the operation data of the tracking aircraft. Among them, the operation data of the tracking aircraft includes the perigee geocentric distance of the tracking aircraft orbit and the apogee geocentric distance of the tracking aircraft orbit. Among them, the simulation data includes simulated satellite orbit data and simulated satellite attitude data. For another example, the processing device 110 can determine the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft. For another example, the processing device 110 can determine whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state. For another example, the processing device 110 can determine the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft.

[0064] The processing device 110 can be local or remote. For example, the processing device 110 can access the information and / or data stored in the terminal device 150 and the memory through the network 120. The processing device 110 can be directly connected to the terminal device 150 and the memory to access the information and / or data stored therein. The processing device 110 can be executed on a cloud platform. For example, the cloud platform can include one or any combination of a private cloud, a public cloud, a hybrid cloud, a community cloud, a distributed cloud, an internal cloud, etc.

[0065] The processing device 110 can include a processor. The processor can process the data and / or information related to the fuel consumption calculation of the relative motion configuration of the water droplet configuration to perform one or more functions described in this application. The processor can include one or more sub-processors (for example, a single-core processing device 110 or a multi-core multi-chip processing device 110). Merely by way of example, the processor can include a central processing unit (CPU), an application-specific integrated circuit (ASIC), an application-specific instruction processor (ASIP), a graphics processing unit (GPU), a physical processing unit (PPU), a digital signal processor (DSP), a field-programmable gate array (FPGA), an editable logic circuit (PLD), a controller, a microcontroller unit, a reduced instruction set computer (RISC), a microprocessor, etc. or any combination of the above.

[0066] The network 120 can facilitate the exchange of data and / or information in a fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration. One or more components in a belly expansion motion analysis device (for example, the processing device 110, the memory, and the terminal device 150) can send data and / or information to other components in a fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration through the network 120. For example, the processing device 110 can receive the detector operation data set by the user through the network 120. The network 120 can be any type of wired or wireless network 120. For example, the network 120 can include a cable network 120, a wired network 120, an optical fiber network 120, a telecommunication network 120, an internal network 120, the Internet 120, a local area network 120 (LAN), a wide area network 120 (WAN), a wireless local area network 120 (WLAN), a metropolitan area network 120 (MAN), a public switched telephone network 120 (PSTN), a Bluetooth network 120, a ZigBee network 120, a near field communication (NFC) network 120, etc. or any combination of the above. The network 120 can include one or more network access points. For example, the network 120 can include wired or wireless network access points, such as base stations and / or Internet exchange points, through which one or more components of a fuel consumption calculation system 100 for the relative motion configuration of the water droplet configuration can be connected to the network 120 to exchange data and / or information.

[0067] The memory can be connected to the network 120 to communicate with one or more components of a relative motion configuration fuel consumption calculation system 100 for a water droplet configuration (e.g., the processing device 110, the terminal device 150, etc.). One or more components of a relative motion configuration fuel consumption calculation system 100 for a water droplet configuration can access the data or instructions stored in the memory through the network 120. The memory can be directly connected to or communicate with one or more components in a relative motion configuration fuel consumption calculation system 100 for a water droplet configuration (such as the processing device 110, the terminal device 150). The memory can be part of the processing device 110. The processing device 110 can also be located in the terminal device 150.

[0068] The terminal device 150 can obtain information or data in a relative motion configuration fuel consumption calculation system 100 for a water droplet configuration. A user (e.g., a researcher) can obtain the process and results of the relative motion configuration fuel consumption calculation for the water droplet configuration through the terminal device 150. The terminal device 150 can include one or any combination of a mobile device, a tablet computer, a laptop computer, etc. The mobile device can include one or any combination of a wearable device, a smart mobile device, a virtual reality device, an augmented reality device, etc. The wearable device can include one or any combination of a smart bracelet, smart shoes and socks, smart glasses, a smart helmet, a smart watch, smart clothing, a smart backpack, smart accessories, a smart handle, etc. The smart mobile device can include one or any combination of a smart phone, a personal digital assistant (PDA), a gaming device, a navigation device, a POS device, etc. The virtual reality device and / or the augmented reality device can include one or any combination of a virtual reality helmet, virtual reality glasses, a virtual reality eye mask, an augmented reality helmet, augmented reality glasses, an augmented reality eye mask, etc.

[0069] It should be noted that the above description is provided for illustrative purposes only and is not intended to limit the scope of the present application. For those of ordinary skill in the art, various changes and modifications can be made under the guidance of the content of the present application. The features, structures, methods, and other features of the exemplary embodiments described in the present application can be combined in various ways to obtain additional and / or alternative exemplary embodiments. For example, the memory can be a data storage device 140 including a cloud computing platform, such as a public cloud, a private cloud, a community cloud, and a hybrid cloud, etc. However, these changes and modifications do not depart from the scope of the present application.

[0070] Please refer to Figure 2 , Figure 2 which shows a flowchart of a relative motion configuration fuel consumption calculation method for a water droplet configuration provided by an embodiment of the present invention. A relative motion configuration fuel consumption calculation method for a water droplet configuration includes the following steps:

[0071] S100. Obtain the operating data of the target aircraft and the operating data of the tracking aircraft. Among them, the operating data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft's orbit and the geocentric distance at the apogee of the tracking aircraft's orbit;

[0072] It can be understood that the above-mentioned operating data of the target aircraft includes the geocentric distance of the target aircraft's operating orbit.

[0073] S200. Determine the relative motion configuration state of the target aircraft and the tracking aircraft based on the operating data of the target aircraft and the operating data of the tracking aircraft;

[0074] Specifically, step S200 also includes;

[0075] When the motion configuration of the target aircraft and the tracking aircraft is specialized into an elliptical configuration, and the fuel consumption for maintaining this configuration is zero at this time;

[0076] When judge whether the target aircraft and the tracking aircraft can form a water droplet configuration;

[0077] Among them, is the geocentric distance at the perigee of the tracking aircraft's orbit, is the geocentric distance at the apogee of the tracking aircraft's orbit, r T is the geocentric distance of the target aircraft's operating orbit.

[0078] S300. Judge whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state;

[0079] Among them, relevant parameters need to be introduced to judge whether the target aircraft and the tracking aircraft can form a water droplet configuration, such as the gravitational constant of the celestial body (here it is the gravitational constant of the earth).

[0080] Step S300 may include the following steps S310 - step S330;

[0081] S310. Determine the semi-major axis, eccentricity, semi-latus rectum, angular velocity at the perigee, and angular velocity at the apogee of the tracking aircraft based on the operating data of the tracking aircraft and the gravitational constant of the celestial body;

[0082] S320. Determine the angular velocity of the target aircraft based on the operating data of the target aircraft and the gravitational constant of the celestial body;

[0083] S330. If the angular velocity at the apogee of the tracking aircraft is greater than the angular velocity of the target aircraft or the angular velocity at the perigee of the tracking aircraft is greater than the angular velocity of the target aircraft, then judge that the target aircraft and the tracking aircraft cannot form a water droplet configuration.

[0084] That is:

[0085] The semi-major axis of the tracking vehicle is:

[0086] The eccentricity of the tracking vehicle is:

[0087] The semi-latus rectum of the tracking vehicle is:

[0088] The angular velocity of the tracking vehicle at perigee is:

[0089] The angular velocity of the tracking vehicle at apogee is:

[0090] The angular velocity of the target vehicle is:

[0091] Wherein, a C is the semi-major axis of the tracking vehicle, e C is the eccentricity of the tracking vehicle, P C is the semi-latus rectum of the tracking vehicle, ω max is the angular velocity of the tracking vehicle at perigee, ω min is the angular velocity of the tracking vehicle at apogee, ω T is the angular velocity of the target vehicle, and μ e is the gravitational constant of the celestial body;

[0092] When ω min > ω T or ω max < ω T a water-drop configuration fly-around configuration cannot be formed.

[0093] S400. If a water-drop configuration can be formed, the fuel consumption for maintaining the configuration is determined based on the operation data of the target vehicle and the operation data of the tracking vehicle.

[0094] Step S400 may include steps S410 - S440.

[0095] Please refer to Figure 4 and Figure 5 , for the maintenance of the relative motion configuration of the water-drop configuration, that is, at the relative motion trajectory direction switching point of the water-drop configuration of the tracking vehicle, by applying a velocity increment once, the magnitude of the velocity at this point remains unchanged, and the direction switches from vector 1 to vector 2 direction, so as to realize the maintenance of the relative motion period of the water-drop configuration. The definitions of the orbital radial direction and the along-track direction are as shown in Figure 5 shown.

[0096] Step S410, determining the smooth point and the direction switching point of the water-drop configuration based on the operation data of the target vehicle and the operation data of the tracking vehicle;

[0097] Step S420: Determine the radial velocity component of the tracking vehicle based on the smooth point and the direction switching point of the water droplet configuration.

[0098] That is:

[0099] When the smooth vertex of the water droplet configuration is at the bottom and the direction switching point is at the top, the radial velocity component v r of the tracking vehicle is

[0100]

[0101] where

[0102] When the smooth vertex of the water droplet configuration is at the top and the direction switching point is at the bottom, the radial velocity component v r of the tracking vehicle is

[0103]

[0104] where

[0105] Step S430: Determine the required velocity increment and the fuel quantity required for a single-stage rocket based on the radial velocity component of the tracking vehicle. The radial velocity component Δv of the tracking vehicle is

[0106] Δv = 2|v r |

[0107] The fuel quantity m fuel required for a single-stage rocket is

[0108]

[0109] where m structure is the airframe weight, P sp is the specific impulse of the engine (in seconds), and g is the acceleration due to gravity.

[0110] Step S440: Determine the fuel consumption for configuration maintenance based on the fuel quantity required for a single-stage rocket, the relative motion period of the water droplet configuration, and the configuration maintenance time.

[0111] That is: When the true anomaly difference Δf down of the tracking vehicle flying from the smooth vertex of the water droplet configuration to the direction switching point of the relative motion trajectory satisfies the following equation

[0112]

[0113] where

[0114]

[0115]

[0116]

[0117]

[0118]

[0119] where Δf down can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf down = 90°, and after Δf down is solved, there is

[0120]

[0121] When the true anomaly difference Δf of the tracking vehicle from the relative motion trajectory direction switching point to the smooth vertex of the water droplet configuration is satisfied up the following equation

[0122]

[0123] where

[0124]

[0125]

[0126]

[0127]

[0128]

[0129] where Δf up can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf up = 90°, and after Δf up is solved, there is

[0130]

[0131] then during the configuration maintenance time, the number of times N of the configuration maintenance control is

[0132]

[0133] then the fuel consumption for configuration maintenance is

[0134]

[0135] Among them, T keep is the setup hold time.

[0136] It should be noted that in the above formula, α, β, s, and c are all reference calculation constants.

[0137] Please refer to Figure 3 , Figure 3 which is a structural block diagram of a fuel consumption calculation system 100 for a relative motion configuration of a water droplet configuration provided by an embodiment of the present invention.

[0138] The data acquisition module 111 of the fuel consumption calculation system 100 for a relative motion configuration of a water droplet configuration is configured to acquire the operation data of a target aircraft and the operation data of a tracking aircraft. Among them, the operation data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft's orbit and the geocentric distance at the apogee of the tracking aircraft's orbit; the configuration state determination module 112 is configured to determine the relative motion configuration state of the target aircraft and the tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft; the judgment module 113 is configured to judge whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state; the calculation module 114 is configured to determine the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft.

[0139] Those skilled in the art should understand that the embodiments of the present invention can be provided as a method, a system, or a computer program product. Therefore, the present invention can take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present invention can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROX, optical storage, etc.) containing computer-usable program code.

[0140] The present invention is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to embodiments of the present invention. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and the combination of flows and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device 110 to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device 110 generate means for implementing the functions specified in Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0141] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus 110 to operate in a particular manner, such that the instructions stored in the computer-readable memory produce a manufacture including an instruction means that implements the functions specified in one or more of the processes Figure 1 one or more processes and / or blocks Figure 1 specified in the block or blocks.

[0142] These computer program instructions can also be loaded onto a computer or other programmable data processing apparatus 110, such that a series of operational steps are performed on the computer or other programmable apparatus to produce a computer-implemented process, whereby the instructions executed on the computer or other programmable apparatus provide steps for implementing the functions specified in one or more of the processes Figure 1 one or more processes and / or blocks Figure 1 specified in the block or blocks.

[0143] Obviously, the above-described embodiments are merely examples for clear illustration and are not intended to limit the implementation. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to exhaustively list all the implementation manners here. And the obvious changes or modifications derived therefrom are still within the protection scope of the present invention.

Claims

1. A calculation method for fuel consumption of a relative motion configuration of a water droplet configuration, characterized in that It includes the following steps: Obtain the operation data of the target aircraft and the operation data of the tracking aircraft. Among them, the operation data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft orbit and the geocentric distance at the apogee of the tracking aircraft orbit; Determine the relative motion configuration state of the target vehicle and the tracking vehicle based on the operating data of the target vehicle and the operating data of the tracking vehicle; including: when , the motion configuration of the target vehicle and the tracking vehicle is specialized into an elliptical configuration, and the fuel consumption for maintaining the configuration is zero at this time; when , determine whether the target vehicle and the tracking vehicle can form a water droplet configuration; where is the geocentric distance at the perigee of the tracking vehicle's orbit, is the geocentric distance at the apogee of the tracking vehicle's orbit, r T is the geocentric distance of the target vehicle's operating orbit; determine the semi-major axis, eccentricity, semi-latus rectum, perigee angular velocity, and apogee angular velocity of the tracking vehicle based on the operating data of the tracking vehicle and the gravitational constant of the celestial body; determine the angular velocity of the target vehicle based on the operating data of the target vehicle and the gravitational constant of the celestial body; if the apogee angular velocity of the tracking vehicle is greater than the angular velocity of the target vehicle or the perigee angular velocity of the tracking vehicle is greater than the angular velocity of the target vehicle, then determine that the target vehicle and the tracking vehicle cannot form a water droplet configuration; the semi-major axis of the tracking vehicle is: The eccentricity of the tracking vehicle is: The semi-latus rectum of the tracking vehicle is: The perigee angular velocity of the tracking vehicle is: The apogee angular velocity of the tracking vehicle is: The angular velocity of the target vehicle is: where, a C is the semi-major axis of the tracking vehicle, e C is the eccentricity of the tracking vehicle, P C is the semi-latus rectum of the tracking vehicle, ω max is the perigee angular velocity of the tracking vehicle, ω min is the apogee angular velocity of the tracking vehicle, ω T is the angular velocity of the target vehicle, μ e is the gravitational constant of the celestial body; Based on the relative motion configuration state, judge whether the target aircraft and the tracking aircraft can form a water droplet configuration; If a water droplet configuration can be formed, determine the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft.

2. The method for calculating fuel consumption of the relative motion configuration of the water droplet configuration according to claim 1, wherein If a water droplet configuration can be formed, in the step of determining the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft, it includes: Determine the smooth point and the direction switching point of the water droplet configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft; Determine the radial velocity component of the tracking aircraft based on the smooth point and the direction switching point of the water droplet configuration.

3. The method for calculating fuel consumption of the relative motion configuration of the water droplet configuration according to claim 2, wherein In the step of determining the smooth point and the direction switching point of the water droplet configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft, it includes: When the smooth vertex of the water droplet configuration is at the bottom and the direction switching point is at the top, and at this time, the radial velocity component v of the tracking aircraft r is Among them, Δf up can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf up = 90°; When the smooth vertex of the water droplet configuration is on the top and the direction switching point is on the bottom, the radial velocity component v of the tracking aircraft r is Among them, Δf down can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf down = 90°.

4. The method for calculating fuel consumption of the relative motion configuration of the water droplet configuration according to claim 3, wherein, In the step of determining the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft, it also includes: Determine the required velocity increment and the amount of fuel required for a single-stage rocket based on the radial velocity component of the tracking vehicle. Among them, the radial velocity component Δv of the tracking vehicle is Δv = 2|v r | The fuel quantity m required for a single-stage rocket fuel is Among them, m structure is the body weight, P sp is the specific impulse of the engine, with the unit of seconds, and g is the acceleration of gravity.

5. The method for calculating fuel consumption of the relative motion configuration of the water droplet configuration according to claim 4, characterized in that, In the step of determining the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft, it also includes: Determine the fuel consumption for maintaining the configuration according to the fuel quantity required by a single-stage rocket, the relative motion period of the water droplet configuration, and the configuration maintenance time.

6. The method for calculating fuel consumption of the relative motion configuration of the water droplet configuration according to claim 5, wherein It also includes the following steps: When the tracking vehicle flies from the smooth vertex of the water droplet configuration to the true anomaly difference Δf at the relative motion trajectory direction switching point down satisfies the following equation Among them, Among them, Δf down can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf down = 90°, after Δf down is calculated, there is When the true anomaly difference Δf of the tracking vehicle flying from the relative motion trajectory direction switching point to the smooth vertex of the water droplet configuration up satisfies the following equation Among them, where Δf up can be numerically solved by the Newton iteration method, and the initial iteration value is selected as Δf up = 90°, after Δf up is calculated, there is Then, during the configuration maintenance time, the number N of configuration maintenance controls is The fuel consumption with configuration retention is where T keep is the setup hold time.

7. A fuel consumption calculation system for the relative motion configuration of a water droplet configuration, characterized in that It includes: A data acquisition module, used to obtain the operation data of the target aircraft and the operation data of the tracking aircraft. Among them, the operation data of the tracking aircraft includes the geocentric distance at the perigee of the tracking aircraft orbit and the geocentric distance at the apogee of the tracking aircraft orbit; A configuration state determination module, configured to determine the relative motion configuration state of a target aircraft and a tracking aircraft based on the operation data of the target aircraft and the operation data of the tracking aircraft; including: when When, the motion configuration of the target aircraft and the tracking aircraft is specialized into an elliptical configuration, and the fuel consumption for maintaining the configuration is zero at this time; when When, it is judged whether the target aircraft and the tracking aircraft can form a water droplet configuration; wherein, Is the geocentric distance of the perigee of the tracking aircraft's orbit, Is the geocentric distance of the apogee of the tracking aircraft's orbit, r T Is the geocentric distance of the target aircraft's operating orbit; determine the semi-major axis, eccentricity, semi-latus rectum, perigee angular velocity and apogee angular velocity of the tracking aircraft based on the operation data of the tracking aircraft and the gravitational constant of the celestial body; determine the angular velocity of the target aircraft based on the operation data of the target aircraft and the gravitational constant of the celestial body; if the apogee angular velocity of the tracking aircraft is greater than the angular velocity of the target aircraft or the perigee angular velocity of the tracking aircraft is greater than the angular velocity of the target aircraft, it is judged that the target aircraft and the tracking aircraft cannot form a water droplet configuration; the semi-major axis of the tracking aircraft is: The eccentricity of the tracking aircraft is: The semi-latus rectum of the tracking aircraft is: The perigee angular velocity of the tracking aircraft is: The apogee angular velocity of the tracking aircraft is: The angular velocity of the target aircraft is: Wherein, a C Is the semi-major axis of the tracking aircraft, e C Is the eccentricity of the tracking aircraft, P C Is the semi-latus rectum of the tracking aircraft, ω max Is the perigee angular velocity of the tracking aircraft, ω min Is the apogee angular velocity of the tracking aircraft, ω T Is the angular velocity of the target aircraft, μ e Is the gravitational constant of the celestial body; A judgment module, used to judge whether the target aircraft and the tracking aircraft can form a water droplet configuration based on the relative motion configuration state; A calculation module, used to determine the fuel consumption for maintaining the configuration based on the operation data of the target aircraft and the operation data of the tracking aircraft.

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